FIELD: aero-space engineering; air start of launch vehicles. SUBSTANCE: method consists in injection of aircraft with launch vehicle to horizontal trajectory in plane of preset orbit of object and acceleration of aircraft to supersonic speed. Then, angle of inclination of trajectory is increased to 10-15 deg for 10 to 20 s. Separation of launch vehicle from aircraft is performed at altitude of 16 to 18 km at speed higher than 2000 km/h. Acceleration of launch vehicle to orbital speed is performed at apogee of transfer ballistic trajectory in repeated start of its third-stage engine. Altitude of apogee of this trajectory is equal to altitude of preset orbit and acceleration rate of launch vehicle is equal to design orbital speed of object. EFFECT: reduced specific power requirements for injection of objects into near-earth orbits. 2 cl, 2 dwg
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